超级军网印度探月卫星明年4月发射
来源：百度文库 编辑：超级军网 时间：2024/04/27 14:01:59
貌似很强大的样子
他们不是有一个世界最大的45X30米天线阵？怎么现在还要建32米天线？
嗯，不错，努力吧。
很 好 很强大。。;P
听说这玩意只有几百公斤
原帖由 spacedog 于 2007-11-23 11:36 发表
他们不是有一个世界最大的45X30米天线阵？怎么现在还要建32米天线？
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需要多点共阵吧？中国目前都有4个固定点的，远洋系列似乎也有类似功能。落月前最少完成6个点。
印度要发射4级大推力火箭，以他自身国家的纬度似乎有些过于浪费:b
而明年4月发射.....我有种不良的预感:Q 南亚次大陆的雨水季节似乎正是那时侯开始的吧
谁知道目前印度最强大的火箭的入轨能力是多少？
原帖由 E网打尽 于 2007-11-25 08:15 发表
谁知道目前印度最强大的火箭的入轨能力是多少？
http://www.war-sky.com/forum/htm_data/18/0711/244012.html
哪位有 月船一号的总重量 燃料重量 和 有效载荷
有的报道显示“印度月船1号”将离月球100公里的轨道上至少飞行2年
为何重量只有几百公斤的情况，带的仪器好像也不比日本中国的少，而且要在100公里轨道上2年？
印度为什么这么强？
有的报道显示“印度月船1号”将离月球100公里的轨道上至少飞行2年
为何重量只有几百公斤的情况，带的仪器好像也不比日本中国的少，而且要在100公里轨道上2年？
印度为什么这么强？
原帖由 zhizunwudi2790 于 2007-11-25 09:17 发表
http://www.war-sky.com/forum/htm_data/18/0711/244012.html
谢谢， 我坚信没有毛子， 印度照样能办事， 当然成不成就另说了。
PSLV-XL 轨道和嫦娥以及辉夜姬差不多
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The spacecraft would be launched by PSLV-XL in a highly elliptical transfer orbit with perigee of about 240 km and an apogee of about 24,000 km. Later, the spacecraft would be raised to moon rendezvous orbit by multiple in-plane perigee maneuvers. These maneuvers would help to achieve the required 3,86,000 km apogee of the Lunar Transfer Trajectory (LTT).
After a quick estimate of the achieved LTT a mid-course correction will be imparted at the earliest opportunity. The spacecraft coasts for about five and a half days in this trajectory prior to the lunar encounter. The major maneuver of the mission, called Lunar Orbit Insertion (LOI) that leads to lunar capture, would be carried out at the peri-selene (nearest point in lunar orbit) leading to successful lunar capture in a polar, near circular 1000 km-altitude orbit.
After successful capture and health checks, the altitude is planned to be lowered through a series of in-plane corrections to achieve the target altitude of 100 km circular polar orbit.
--------------------------------
The spacecraft would be launched by PSLV-XL in a highly elliptical transfer orbit with perigee of about 240 km and an apogee of about 24,000 km. Later, the spacecraft would be raised to moon rendezvous orbit by multiple in-plane perigee maneuvers. These maneuvers would help to achieve the required 3,86,000 km apogee of the Lunar Transfer Trajectory (LTT).
After a quick estimate of the achieved LTT a mid-course correction will be imparted at the earliest opportunity. The spacecraft coasts for about five and a half days in this trajectory prior to the lunar encounter. The major maneuver of the mission, called Lunar Orbit Insertion (LOI) that leads to lunar capture, would be carried out at the peri-selene (nearest point in lunar orbit) leading to successful lunar capture in a polar, near circular 1000 km-altitude orbit.
After successful capture and health checks, the altitude is planned to be lowered through a series of in-plane corrections to achieve the target altitude of 100 km circular polar orbit.
设备不少，这么轻的质量，携带了不少设备，当然很多设备来自美国和欧洲
印度现在的发射能力也还可以，对这样的任务应该可以承担
当然失败也很正常
------------------------------------------------------------------------------
Scientific Payloads
Chandrayaan-1 is an Indian Mission to the Moon. The indigenously developed payload/ experiments are:
TMC
Terrain Mapping stereo Camera (TMC) in the panchromatic band, having 5 m spatial resolution and 20 km swath
Read More..
HySI
Hyper Spectral Imaging camera (HYSI) operating in 400-950nm band with a spectral resolution of 15nm and spatial resolution of 80m with a swath of 20km.
Read More..
LLRI
Lunar Laser Ranging Instrument (LLRI) with height resolution of about 10m
Read More..
HEX
High Energy X-ray spectrometer (HEX) using Cadmium-Zinc-Telluride (CdZnTe) detector in the 30-250 keV energy region with spatial resolution of 40km
Read More..
MIP
Moon Impact Probe (MIP) as piggyback on the main orbiter of the Chandrayaan-1 spacecraft which will impact on the surface of the moon
Read More..
Apart from the above indigenous payloads/experiments, ISRO solicited proposals through an Announcement of Opportunity (AO) from International and Indian Scientific Community for participating in the mission by providing suitable scientific payloads complementing the Chandrayaan-1 objectives. Out of the proposals received, six experiments were finally selected for inclusion in Chandrayaan-1 mission. The AO payloads on-board Chandrayaan-1 are:
C1XS
Chandrayaan-1 X-ray Spectrometer (C1XS) through ESA -a collaboration between Rutherford Appleton Laboratory, UK and ISRO Satellite Centre, ISRO. Part of this payload is redesigned by ISRO to suit Chandrayaan-1 scientific objectives.
Read More..
SIR-2
Near Infra Red spectrometer (SIR-2) from Max Plank Institute, Lindau, Germany through ESA
Read More..
SARA
Sub KeV Atom Reflecting Analyser (SARA) through ESA, from Swedish Institute of Space Physics, Sweden and Space Physics Laboratory, Vikram Sarabhai Space Centre, ISRO. The Data Processing Unit of this payload/ experiment is designed and developed by ISRO, while Swedish Institute of Space Physics develops the payload.
Read More..
RADOM
Radiation Dose Monitor Experiment (RADOM) from Bulgarian Academy of Sciences
Read More..
MiniSAR
Miniature Synthetic Aperture Radar (MiniSAR) from Applied Physics Laboratory, Johns Hopkins University and Naval Air Warfare Centre, USA through NASA
Read More..
M3
Moon Mineralogy Mapper (M3) from Brown University and Jet Propulsion Laboratory, USA through NASA
Read More..
印度现在的发射能力也还可以，对这样的任务应该可以承担
当然失败也很正常
------------------------------------------------------------------------------
Scientific Payloads
Chandrayaan-1 is an Indian Mission to the Moon. The indigenously developed payload/ experiments are:
TMC
Terrain Mapping stereo Camera (TMC) in the panchromatic band, having 5 m spatial resolution and 20 km swath
Read More..
HySI
Hyper Spectral Imaging camera (HYSI) operating in 400-950nm band with a spectral resolution of 15nm and spatial resolution of 80m with a swath of 20km.
Read More..
LLRI
Lunar Laser Ranging Instrument (LLRI) with height resolution of about 10m
Read More..
HEX
High Energy X-ray spectrometer (HEX) using Cadmium-Zinc-Telluride (CdZnTe) detector in the 30-250 keV energy region with spatial resolution of 40km
Read More..
MIP
Moon Impact Probe (MIP) as piggyback on the main orbiter of the Chandrayaan-1 spacecraft which will impact on the surface of the moon
Read More..
Apart from the above indigenous payloads/experiments, ISRO solicited proposals through an Announcement of Opportunity (AO) from International and Indian Scientific Community for participating in the mission by providing suitable scientific payloads complementing the Chandrayaan-1 objectives. Out of the proposals received, six experiments were finally selected for inclusion in Chandrayaan-1 mission. The AO payloads on-board Chandrayaan-1 are:
C1XS
Chandrayaan-1 X-ray Spectrometer (C1XS) through ESA -a collaboration between Rutherford Appleton Laboratory, UK and ISRO Satellite Centre, ISRO. Part of this payload is redesigned by ISRO to suit Chandrayaan-1 scientific objectives.
Read More..
SIR-2
Near Infra Red spectrometer (SIR-2) from Max Plank Institute, Lindau, Germany through ESA
Read More..
SARA
Sub KeV Atom Reflecting Analyser (SARA) through ESA, from Swedish Institute of Space Physics, Sweden and Space Physics Laboratory, Vikram Sarabhai Space Centre, ISRO. The Data Processing Unit of this payload/ experiment is designed and developed by ISRO, while Swedish Institute of Space Physics develops the payload.
Read More..
RADOM
Radiation Dose Monitor Experiment (RADOM) from Bulgarian Academy of Sciences
Read More..
MiniSAR
Miniature Synthetic Aperture Radar (MiniSAR) from Applied Physics Laboratory, Johns Hopkins University and Naval Air Warfare Centre, USA through NASA
Read More..
M3
Moon Mineralogy Mapper (M3) from Brown University and Jet Propulsion Laboratory, USA through NASA
Read More..
印度比较有趣的是携带了一台来自美国的小型合成孔径雷达（mini-SAR）
---------------------------------------------------------
Miniature Synthetic Aperture Radar (MiniSAR)
Scientific Objectives:
To detect water ice in the permanently shadowed regions on the Lunar poles up to a depth of a few meters
Although returned lunar samples show the Moon to be exceedingly dry, recent discoveries suggest that water–ice may exist in the polar regions. Because its axis of rotation is perpendicular to the ecliptic plane, the poles of the Moon contain areas that are permanently dark. This results in the creation of “cold traps”, zones that, because they are never illuminated by the sun, may be as cold as 50–70 K. Cometary debris and meteorites containing water-bearing minerals constantly bombard the Moon. Most of this water is lost to space, but if a water molecule finds its way into a cold trap, it is there for ever – no physical process is known that can remove it. Over geological time, significant quantities of water could accumulate.
In 1994, the Clementine polar-orbiting spacecraft used its radio transmitter to “illuminate” these dark, cold trap areas; echoes were recorded by the radio antennas of the Earth-based Deep Space Network. Analysis of one series of data indicated that at least some of the dark regions near the South Pole had reflections that mimicked the radio-scattering behavior of ice. Subsequently, the orbiting Lunar Prospector spacecraft found large quantities of hydrogen in the polar regions, corresponding closely with large areas of permanent shadow, consistent with the presence of water ice. The controversy over lunar polar ice continues to this day.
Mini-SAR is a onboard radar mapper that will allow viewing of all permanently shadowed areas on the Moon, regardless of whether sunlight is available or the angle is not satisfactory. Mini–SAR will observe these areas at incidence angles near 45 degrees, recording echoes in both orthogonal senses of received polarization, allowing ice to be optimally distinguished from dry lunar surface.
Payload Configuration Details:
The mini-SAR system will transmit Right Circular Polarization (RCP) and receive both Left Circular Polarization (LCP) and RCP. In scatterometer mode, the system will measure the RCP and LCP response in the altimetry footprint along the nadir ground-track. In radiometer mode, the system will measure the surface RF emissivity, allowing a determination of the near normal incidence Fresnel reflectivity.
The synthetic aperture radar system works at a frequency 2.38 GHz with a resolution of 75m per pixel and weighs 6.5kg.
Miniature Synthetic Aperture Radar (MiniSAR) is from Applied Physics Laboratory, Johns Hopkins University and Naval Air Warfare Centre, USA through NASA.
---------------------------------------------------------
Miniature Synthetic Aperture Radar (MiniSAR)
Scientific Objectives:
To detect water ice in the permanently shadowed regions on the Lunar poles up to a depth of a few meters
Although returned lunar samples show the Moon to be exceedingly dry, recent discoveries suggest that water–ice may exist in the polar regions. Because its axis of rotation is perpendicular to the ecliptic plane, the poles of the Moon contain areas that are permanently dark. This results in the creation of “cold traps”, zones that, because they are never illuminated by the sun, may be as cold as 50–70 K. Cometary debris and meteorites containing water-bearing minerals constantly bombard the Moon. Most of this water is lost to space, but if a water molecule finds its way into a cold trap, it is there for ever – no physical process is known that can remove it. Over geological time, significant quantities of water could accumulate.
In 1994, the Clementine polar-orbiting spacecraft used its radio transmitter to “illuminate” these dark, cold trap areas; echoes were recorded by the radio antennas of the Earth-based Deep Space Network. Analysis of one series of data indicated that at least some of the dark regions near the South Pole had reflections that mimicked the radio-scattering behavior of ice. Subsequently, the orbiting Lunar Prospector spacecraft found large quantities of hydrogen in the polar regions, corresponding closely with large areas of permanent shadow, consistent with the presence of water ice. The controversy over lunar polar ice continues to this day.
Mini-SAR is a onboard radar mapper that will allow viewing of all permanently shadowed areas on the Moon, regardless of whether sunlight is available or the angle is not satisfactory. Mini–SAR will observe these areas at incidence angles near 45 degrees, recording echoes in both orthogonal senses of received polarization, allowing ice to be optimally distinguished from dry lunar surface.
Payload Configuration Details:
The mini-SAR system will transmit Right Circular Polarization (RCP) and receive both Left Circular Polarization (LCP) and RCP. In scatterometer mode, the system will measure the RCP and LCP response in the altimetry footprint along the nadir ground-track. In radiometer mode, the system will measure the surface RF emissivity, allowing a determination of the near normal incidence Fresnel reflectivity.
The synthetic aperture radar system works at a frequency 2.38 GHz with a resolution of 75m per pixel and weighs 6.5kg.
Miniature Synthetic Aperture Radar (MiniSAR) is from Applied Physics Laboratory, Johns Hopkins University and Naval Air Warfare Centre, USA through NASA.
任务是探测月球上的水冰
印度神油效果真不错，估计还会延迟更久才射。;P :D
原帖由 sexthegun 于 2007-11-25 03:50 发表
=================================
需要多点共阵吧？中国目前都有4个固定点的，远洋系列似乎也有类似功能。落月前最少完成6个点。
印度要发射4级大推力火箭，以他自身国家的纬度似乎有些过于浪费:b
而明年 ...
雨季一般是7－9月。
月船1号全重好象是1.05吨
将近一半是燃料，嫦娥也差不多。
原帖由 songfq 于 2007-11-25 21:09 发表
月船1号全重好象是1.05吨